Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 141
... equilibrium values at about 25 % of the shock- layer thickness from the shock wave . For the equilibrium case , the influence of precursor heating on shock - layer temperature , pressure , and density variations is discussed in Ref . 2 ...
... equilibrium values at about 25 % of the shock- layer thickness from the shock wave . For the equilibrium case , the influence of precursor heating on shock - layer temperature , pressure , and density variations is discussed in Ref . 2 ...
Page 142
... equilibrium condition . The results of equilibrium and nonequilibrium radiative flux toward the body ( along the stagnation line ) are illustra- ted in Fig . 10. Although it is realistic to calculate the radiative flux based on the ...
... equilibrium condition . The results of equilibrium and nonequilibrium radiative flux toward the body ( along the stagnation line ) are illustra- ted in Fig . 10. Although it is realistic to calculate the radiative flux based on the ...
Page 144
... EQUILIBRIUM 0.002 0 0.2 0.4 0.6 Q8 10 € = x2 / R 0.8 Fig . 11 Variation of radiative and convective heat flux with distance along the body surface . the body is significantly higher than equilibrium heating . Results similar to this ...
... EQUILIBRIUM 0.002 0 0.2 0.4 0.6 Q8 10 € = x2 / R 0.8 Fig . 11 Variation of radiative and convective heat flux with distance along the body surface . the body is significantly higher than equilibrium heating . Results similar to this ...
Contents
Effects of Atmospheric Structure on Radiative Heating | 3 |
Radiative Flux Penetration through a Blown Shock Layer | 22 |
Approximate Inviscid Radiating Flowfield Analysis | 42 |
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ablation absorption coefficient AIAA AIAA Journal AIAA Paper altitudes analysis angle of attack base blockage body surface boundary layer bow shock calculations carbon phenolic chemical chemical equilibrium computed configuration correlation distribution energy enthalpy entry conditions equilibrium experimental flow flowfield freestream graphite H₂ heat shield Heat Transfer heat-transfer hydrogen hyperboloid inertial entry angle intensity inviscid Jupiter Jupiter entry km/sec laminar laser mass loss mass transfer material mixture model atmospheres MW/m² NASA nominal nondimensional nonequilibrium number density obtained Outer Planet Entry parameters PRECURSOR EFFECT precursor heating precursor region predicted present pressure radiation radiative and convective radiative flux radiative heat flux radiative heating rates recession Reynolds number shock-layer shown in Fig silica solution species spectral spectral flux sphere-cone stagnation point stagnation-point temperature thermal thermochemical thermodynamic tion trajectory turbulent uncertainty variation velocity viscous shock-layer VSL3D wall